This article reviews research into the potential of vortex generators to mitigate shock-induced separation. Studies ranging from those conducted in the early post-war era to those performed recently are discussed. On the basis of the investigations described in this report, it is clear that vortex generators can alleviate shock-induced boundary layer separation. Yet, it will be shown that their potential and efficiency varies considerably in practical applications. Much more success is reported in transonic test cases compared to separation induced in purely supersonic interactions. Under a variety of flow conditions, the best performance is achieved with vortex generators with a height of roughly half the boundary layer thickness and a shape similar to a swept vane. Notwithstanding this, vortex generator performance is not as consistent as it is in low-speed applications. Further work is required before vortex generators can be implemented into the design process for eliminating shock-induced separation on transonic wings and in supersonic inlets.

/pdf/a-review-of-the-use-of-vortex-generators-for-mitigating-3eb2zlxx8d.pdf

A review of the use of vortex generators for mitigating shock-induced separation

Secondary flow limits the aerodynamic loading level of turbomachinery. Vortex generators (VGs) offer the potential to attenuate secondary flow when implemented at the endwall of the blade passage. Customary design usually relies on computational fluid dynamics (CFD); however, VG geometry modeling and mesh generation are challenging. This paper presents an efficient method for designing the optimal VG layout. In this approach, first, a mathematical model (BAYC) is introduced to replace the actual VGs; hence, simulation can be carried out without detailed VG gridding. Second, an optimization procedure with response surface methods is employed to determine the optimal VG layout. To illustrate the proposed method, compressor cascades with one and three VGs are used as the test cases. The results demonstrate that the optimal VG layout may effectively weaken the secondary flow and can decrease the aerodynamic loss by 15–25% in almost all incidence angle ranges, particularly at positive incidence angles. Flow mechanism analysis indicates that VGs can enhance the boundary layer kinetic energy, thereby elevating the capability to withstand adverse pressure gradients.

Efficient Design Method for Applying Vortex Generators in Turbomachinery

In this work computational models were developed and used to investigate applications of vortex generators (VGs) to turbomachinery. The work was aimed at increasing the efficiency of compressor components designed for the NASA Ultra Efficient Engine Technology (UEET) program. Initial calculations were used to investigate the physical behavior of VGs. A parametric study of the effects of VG height was done using 3-D calculations of isolated VGs. A body force model was developed to simulate the effects of VGs without requiring complicated grids. The model was calibrated using 2-D calculations of the VG vanes and was validated using the 3-D results. Then three applications of VGs to a compressor rotor and stator were investigated: 1) The results of the 3-D calculations were used to simulate the use of small casing VGs used to generate rotor preswirl or counterswirl. Computed performance maps were used to evaluate the effects of VGs. 2) The body force model was used to simulate large part-span splitters on the casing ahead of the stator. Computed loss buckets showed the effects of the VGs. 3) The body force model was also used to investigate the use of tiny VGs on the stator suction surface for controlling secondary flows. Near-surface particle traces and exit loss profiles were used to evaluate the effects of the VGs.

/pdf/computational-modeling-of-vortex-generators-for-53auqh7i9c.pdf

Computational Modeling of Vortex Generators for Turbomachinery

Influence of sub boundary layer vortex generator height and attack angle on cross-flows in the hub region of compressors

: Two dimensional fully-mixed-out flow conditions were measured downstream of a two-passage transonic fan-blade cascade which had low-profile vortex generators (VGs) attached to the suction surfaces of the blades. The simulation was conducted using a blowdown wind tunnel at a Mach number of 1.4. The objective was to assess the effects of vortex generating devices on the suction surface shock-boundary layer interaction and the resulting losses. Measurements are reported from tests made with older aluminum blading, with and without VGs, and with a nominally similar new set of steel blading, with and without VGs. Differences between the old and new blading were found to be most significant. While shock structures appeared to be similar with VGs attached, dye injection showed that the shock-induced boundary layer separation was greatly suppressed and the downstream flow was much steadier. With VGs, the flow turning was improved by 0.94 degrees, but the flow loss coefficient increased by about 8%. An extension of the study is needed to fully assess the potential of using low-profile VGs in military fan engines. (AN)

The effects of low-profile vortex generators on flow in a transonic fan-blade cascade

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The effects of low-profile vortex generators on flow in a transonic fan-blade cascade